CN114383934B - Landing gear hook ring lock ring test loading device and method - Google Patents
Landing gear hook ring lock ring test loading device and method Download PDFInfo
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- CN114383934B CN114383934B CN202210035789.9A CN202210035789A CN114383934B CN 114383934 B CN114383934 B CN 114383934B CN 202210035789 A CN202210035789 A CN 202210035789A CN 114383934 B CN114383934 B CN 114383934B
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01N—INVESTIGATING OR ANALYSING MATERIALS BY DETERMINING THEIR CHEMICAL OR PHYSICAL PROPERTIES
- G01N3/00—Investigating strength properties of solid materials by application of mechanical stress
- G01N3/02—Details
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01N—INVESTIGATING OR ANALYSING MATERIALS BY DETERMINING THEIR CHEMICAL OR PHYSICAL PROPERTIES
- G01N3/00—Investigating strength properties of solid materials by application of mechanical stress
- G01N3/02—Details
- G01N3/04—Chucks
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01N—INVESTIGATING OR ANALYSING MATERIALS BY DETERMINING THEIR CHEMICAL OR PHYSICAL PROPERTIES
- G01N3/00—Investigating strength properties of solid materials by application of mechanical stress
- G01N3/08—Investigating strength properties of solid materials by application of mechanical stress by applying steady tensile or compressive forces
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Abstract
The invention discloses a landing gear hook ring lock ring test loading device and a landing gear hook ring lock ring test loading method. The device comprises a loading joint and a loading adapter; a matching groove (5-3) is formed in the loading connector, a loading plane (5-5) is formed in the bottom of the matching groove, the matching groove is used for clamping and fixing a lock ring of the shackle lock, the loading plane is in contact fit with the outer circular surface of the lock ring, and the loading connector is matched with the inner side surface (1-1) of the landing gear lock column support (1); the loading adapter comprises an upper adapter (8) and a lower adapter (11), the upper adapter and the lower adapter are connected into a whole relatively, a landing gear belt lock seat ((1)) of the landing gear lock column support is arranged in a space formed by surrounding the upper adapter and the lower adapter, the upper adapter is hinged with the loading connector through a first hinge shaft (5-1), the lower adapter is hinged with one end of a force transducer (12), and the other end of the lower adapter is connected with a servo cylinder (14) through a steel wire rope (13).
Description
Technical Field
The invention relates to a landing gear shackle lock ring loading test, in particular to a landing gear shackle lock ring test loading device and method.
Background
The shackle lockset has the characteristics of convenient installation, convenient and reliable locking and unlocking, strong applicability to the use environment and the like. Thus, currently, hook and loop locks are commonly used for aircraft landing gear down locks and up locks. The locking hook of the lock is arranged on the structure of the aircraft body, and the locking ring on the landing gear moving member is hooked through the locking hook, so that the moving member is fixed at a required position. The safety and reliability of these hook and loop locks on aircraft landing gear are directly related to the safety and reliability of the aircraft, so that the airworthiness requires that the strength of important parts such as the lock ring be tested and verified.
The lock ring on the landing gear moving member is generally designed into a support with a lock column structure, and the lock column structure is realized by fixing a lock column bolt or a lock column bolt on the support after penetrating through the roller and then fixing the lock column structure on the support by a nut. The outer surfaces of the lock stud and the roller are generally cylindrical surfaces or ellipsoids so as to improve the unlocking and locking reliability. The contact surface of the lock hook and the lock column is generally a plane, so that after locking, the lock column and the lock hook are in line contact connection or point contact. In order to simulate the actual stress of the locking ring in the using process, the locking ring structure usually carries out a loading test along with the landing gear (without a lock), so that a test loading device is required to be designed to simulate the load of the locking ring in the actual using process. Therefore, the loading device for the lock ring strength test needs to ensure that the lock ring and the lock hook are in a mounting connection mode, and the loading direction and loading of the lock ring are smoothly carried out.
In order to meet the requirements of the installation connection form and load application, a set of locking ring test loading device is required to be designed, and the locking ring is simulated to act on the locking ring. When the lock hook acts on the lock column and the acting force direction points to the lock seat base, the existing lock ring test loading device can only be hard-connected with one side of the lock seat, and pushing load is applied to the lock column. The loading mode has a complex structure, and the loading load is not accurately controllable.
Disclosure of Invention
Aiming at the defects of the existing landing gear-free hook ring lock test loading device, the invention provides the landing gear hook ring lock ring test loading device and the landing gear hook ring lock ring test loading method, the load applied by the device can simulate the load applied to the hook ring in the actual use process more truly, and meanwhile, the landing gear hook ring test loading device has the advantages of simple structure, convenience in installation and use and the like, and the test cost is reduced while the strength test efficiency and the precision of the hook ring lock ring are improved.
In order to solve the technical problems, the invention adopts the following technical scheme:
a landing gear shackle lock loop test loading device, comprising a loading joint and a loading adapter;
the loading connector comprises a loading adapter and a matching plate, wherein a matching groove is formed in the loading adapter, a loading plane is arranged at the bottom of the matching groove, the matching plate is detachably connected with the loading adapter and fixes a lock ring of a hook ring lock in the matching groove, the loading plane is in contact fit with the outer circular surface of the lock ring, a first side surface of the loading adapter perpendicular to the axis of the lock ring is matched with the inner side surface of a landing gear lock column support, and the width of the loading plane along the axial direction of the lock ring is consistent with the width of a lock hook of the hook ring lock;
the loading adaptor comprises an upper adaptor and a lower adaptor, the upper adaptor and the lower adaptor are oppositely arranged and are detachably connected into a whole, the landing gear belt lock of the landing gear lock column support is arranged in a space formed by encircling the upper adaptor and the lower adaptor, the upper adaptor is hinged with the loading joint through a first hinge shaft, the lower adaptor is hinged with one end of a force transducer, and the other end of the force transducer is connected with a servo cylinder through a steel wire rope.
The invention simulates the load-bearing mode (line-surface contact, point-surface contact or surface-surface contact) of the shackle lock hook and the shackle of a real landing gear, the force acting point and acting direction of the shackle are adjustable, the shackle lock shackle is wound around the shackle lock shackle fastening component structure through the loading adapter to block, and meanwhile, the shackle is pulled and loaded through the servo cylinder, so that the test loading efficiency and precision are improved, and the test cost is reduced.
Preferably, a fixed pulley assembly is arranged below the near servo cylinder end of the steel wire rope, and comprises a fixed pulley for supporting the steel wire rope, a pulley support for mounting the fixed pulley, a pulley height adjusting plate arranged below the pulley support, and a pulley support fixing upright post arranged below the pulley height adjusting plate.
Preferably, the two ends of the loading adapter are provided with first end faces, the two sides of the loading adapter are provided with first side faces, the outer sides of the first end faces are provided with the first hinge shafts, and the first side faces are vertically provided with the matching grooves.
Preferably, the front end of the cooperation recess sets up the cooperation terminal surface, the middle part of cooperation board sets up spacing boss, just the nearly cooperation recess face of spacing boss sets up spacing cambered surface, spacing boss card is gone into the cooperation recess, just the side of spacing boss with the cooperation of cooperation terminal surface, spacing cambered surface with the cooperation of cooperation recess forms the spacing space of catch.
Preferably, the middle inner side of the upper adaptor is provided with a loading joint mounting groove, two sides of the loading joint mounting groove are respectively provided with a first hinge shaft mounting groove, an external mounting adaptor limiting clamp of the loading joint mounting groove is arranged at one end of the adaptor limiting clamp, the first hinge shaft is arranged in a mounting space formed by matching the first hinge shaft mounting groove with the first hinge shaft limiting cylindrical surface, and the loading joint and the upper adaptor are hinged into a whole through the first hinge shaft.
Based on the same inventive concept, the invention also provides a locking ring loading experiment method using the landing gear locking ring experiment loading device, which comprises the following specific steps:
loading the landing gear with the lock seat into a space formed by surrounding the upper adapter and the lower adapter, clamping a lock ring on a landing gear lock column support into a matching groove of a loading head assembly, enabling a loading plane in the matching groove to be in contact fit with the outer circular surface of the lock ring, and designing the distance L between the contact point of the loading plane and the lock ring and the first side surface of the loading adapter according to the requirement so as to simulate the contact form of the lock ring in the actual use process;
the position and the height of the fixed pulley assembly are adjusted to adjust the position of a tangent point of the steel wire rope and the fixed pulley relative to a lock cylinder loading point, so that the adjustment of an included angle alpha between lateral projection lines of the lock ring axis direction B and the loading direction D is realized, the adjustment of an included angle beta between a projection line of the lock cylinder support stress direction C and the loading direction D on a loading plane is realized, and finally, the loading direction D meets the test requirement;
the servo cylinder pulls the load cell through a wire rope, the load cell pulls the load adapter, and applies a load to the lock ring through the load joint.
The main technical characteristics of the scheme of the invention are as follows:
A. the loading adapter is hinged with the lock cylinder in the lock ring:
the limiting boss of the matching plate in the loading joint is inserted into the matching groove in the loading adapter, and the locking ring (roller) is clamped in the limiting boss; the loading plane of the loading adapter is in contact fit with the outer surface of the lock ring, the axial width of the loading plane of the loading adapter is consistent with the lock hook of the shackle lock along the lock ring, the contact form between the lock hook of the shackle lock and the lock ring in the using process is simulated, and the contact form can be point-surface contact or line-surface contact; the loading adapter is perpendicular to the planes on two sides of the axis of the shackle lock ring and is matched with the inner side surface of the lock ring, the distance between the loading plane of the loading adapter and the planes on two sides of the axis of the shackle lock perpendicular to the lock ring along the axial direction of the lock ring is consistent with the corresponding distance between the planes of the lock hook and the planes on two sides of the axis of the shackle lock perpendicular to the lock ring, and the loading position of the lock hook on the lock ring is simulated; the limiting matching surface on the limiting boss is in contact fit with the outer surface of the locking ring, so that the translation of the adapter around the plane vertical to the axis of the locking ring is limited; and connecting the matched loading adapter with the matching plate by using a set screw.
B. The loading adapter is hinged with the loading adapter:
the two sides of the loading adapter are provided with first hinge shafts along the direction vertical to the axis of the lock cylinder, and the first hinge shafts are placed in first hinge shaft mounting grooves of the upper adapter; the adapter limiting clamp is connected with the upper adapter to limit the first hinge shaft in the first hinge shaft mounting groove; after the adapter limiting clamp is matched with the upper adapter, the upper adapter is connected with the upper adapter through an adapter limiting clamp screw; the loading adapter is hinged with the loading adapter, the rotation freedom degree of the loading adapter around the axis of the first hinge shaft is released, the additional bending moment brought to the locking ring due to the deviation of the loading direction is prevented, and therefore the accuracy of the test is improved.
C. The loading adapter realizes the adapter:
the upper adapter piece is connected with the lower adapter piece through bolts after bypassing the service environment structural obstacle, and the loading adapter piece loads the locking ring by utilizing pulling force, so that the scheme that the locking ring is loaded in a pushing mode due to the service environment structural obstacle is avoided.
The lower adapter is connected with the force measuring sensor, and the force measuring sensor is connected with the servo cylinder through the fixed pulley by using the steel wire rope: one end of the force transducer is hinged with the lower adapter, and the other end of the force transducer is connected with the steel wire rope; the steel wire rope bypasses the fixed pulley and then changes direction to be connected with the servo cylinder.
D. The fixed pulley component is connected with the steel wire rope:
the pulley support is fixedly connected with the pulley support fixing upright post, and the position of the pulley support fixing upright post is adjusted so that the axis of the locking ring is in a symmetrical plane of the fixed pulley perpendicular to the rotating shaft of the fixed pulley; the height of the pulley support fixed upright post is adjusted, so that the direction of the wire rope which does not pass through the fixed pulley section is consistent with the direction of the applied load required by the test; the adjustment of different loading directions is realized by adjusting the position and the height of the pulley support fixing upright post.
The landing gear hook ring lock ring test loading device is suitable for the hook ring lock ring strength test loading, and mainly has the following three outstanding advantages:
1. the application is wide, and the method can be used for loading various shackle lock contact forms.
The invention can be suitable for the strength test loading of various hook-and-loop lock cylinders (the outer surface of the lock cylinder or the lock cylinder roller can be a cylindrical surface, a spherical surface or an ellipsoidal surface) by only changing the loading plane and the matching groove of the loading adapter.
2. The load of the lock ring in the actual use process is simulated more truly.
The loading adapter simulates the contact form of the lock hook plane and the lock column and the loaded position of the lock column; the adjustment and simulation of the loading direction are realized by adjusting the contact point position of the steel wire rope and the fixed pulley.
The cylindrical first hinge shaft arranged on the outer side of the loading adapter is hinged with the loading adapter, so that the rotation freedom degree around the first hinge shaft is released, and the additional bending moment brought to the locking ring due to the deviation of the loading direction is avoided during loading.
3. The locking ring is pulled and loaded (instead of pushed and loaded) through the switching, so that the test precision is improved, and the test loading difficulty is reduced.
In the prior art, in order to check the strength of the hook-and-loop lock seat, the hook-and-loop lock seat is installed on a locked component to carry out a loading test, and in order to avoid the structural obstruction of the component, a push-and-push mode is generally adopted to load the lock ring, so that the loading direction is not easy to keep, the test quality is influenced, the loading scheme is complex, and the test cost and the test difficulty are increased. According to the scheme, the switching mode is adopted to wind the structural obstacle of the unlocking seat connecting part, so that the locking ring is always pulled in the loading direction, the test loading difficulty is reduced, and the test precision is improved.
Drawings
In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the drawings that are required in the embodiments or the description of the prior art will be briefly described, and it is obvious that the drawings in the following description are some embodiments of the present invention, and other drawings may be obtained according to these drawings without inventive effort for a person skilled in the art.
FIG. 1 is a three-dimensional view of the general structure of the landing gear hook and loop lock loop test loading device of the present invention.
FIG. 2 is a side view of the general construction of the landing gear hook ring lock loop test loading device of the present invention.
Fig. 3 is a view in the direction a of fig. 2.
Fig. 4 is an exploded view of the landing gear with a lock base.
Fig. 5 is an exploded view of the load joint.
Fig. 6 is a diagrammatic view of the components of the loading adapter.
FIG. 7 is an exploded view of the load control assembly.
Fig. 8 is an exploded view of the fixed sheave assembly.
Fig. 9 is a schematic structural view of the roller.
Fig. 10 is a front view of a loading adapter.
Fig. 11 is a bottom view of the loading adapter.
Fig. 12 is a schematic three-dimensional structure of the mating board.
Fig. 13 is a schematic three-dimensional structure of the upper adapter.
Fig. 14 is a schematic three-dimensional structure of the adapter limiting card.
Fig. 15 is a schematic three-dimensional structure of the lower adaptor.
In the figure:
(1) landing gear with lock seat, (2) loading joint, (3) loading adapter, (4) loading control component, and (5) fixed pulley component.
B. The axial direction of the lock cylinder, the stress direction of the lock cylinder support, the loading direction, the front-back adjustment direction of the pulley, the height adjustment direction of the pulley, the left-right adjustment direction of the pulley, and the loading point O 1 Distance from the first side of the loading adapter.
And alpha, an included angle between the axial direction B of the lock cylinder and the lateral projection line of the loading direction D, and beta, an included angle between the stress direction C of the lock cylinder support and the projection line of the loading direction D on the loading plane.
O 1 Lock cylinder loading point, O 2 And the tangent point of the steel wire rope and the pulley.
1. Landing gear lock cylinder support 1-1, inboard side 2, lock stud 3, roller, 3-1, outboard arc, 3-2, roller axle bore, 4, lock cylinder nut, 5, load adapter, 5-1, first articulation axle, 5-2, first end face, 5-3, mating recess, 5-4, mating end face, 5-5, load plane, 5-6, first threaded bore, 5-7, first side, 6, mating plate, 6-1, second threaded bore, 6-2, limit boss, 6-3, limit arc, 7, first screw, 8, upper adapter, 8-1, first articulation axle mounting groove, 8-2, third threaded bore, 8-3, first lug, 8-4, load adapter mounting groove, 9, adapter limit clip, 9-1, adapter limit clip screw, 9-2, limit clip end face, 9-3, first articulation axle limit cylinder face, 10, adapter limit clip, 11, lower adapter 11, 11-1, second lug 11, third lug 11, third lug, 13, second lug, third lug, 14, second lug, third lug, and fixed pulley, 13, support 16.
Detailed Description
The invention is further described below in connection with specific preferred embodiments, but it is not intended to limit the scope of the invention.
For convenience of description, the relative positional relationship of the components, such as: the descriptions of the upper, lower, left, right, etc. are described according to the layout directions of the drawings in the specification, and do not limit the structure of the present patent.
As shown in FIG. 1, one embodiment of the landing gear hook and loop lock ring test loading device of the present invention includes a loading adapter (2), a loading adapter (3), a loading control assembly (4), and a fixed sheave assembly (5).
As shown in fig. 4 and 9, in this embodiment, a landing gear lock cylinder support 1 is mounted on a landing gear lock seat (only part of landing gear is shown) (1) related to the landing gear hook ring lock ring test loading device of the present invention, a roller 3 is mounted on the landing gear lock cylinder support 1 through matching of a lock cylinder bolt 2 and a lock cylinder nut 4, and an outer circular surface of the roller 3 is set as an outer cambered surface 3-1 along a roller axis. However, it should be noted that the landing gear shackle locking ring test loading device of the present invention is not limited to use with such a lock ring formed by a stud and a roller, and is also applicable to other types of shackle locking rings existing in the industry, such as only a stud.
As shown in fig. 5, the loading connector (2) comprises a loading adapter 5 and a mating plate 6. As shown in fig. 10 and 11, the loading adapter 5 includes a first end surface 5-2 located at two ends and a first side surface 5-7 located at two sides, a first hinge shaft 5-1 is disposed on the outer side of the first end surface 5-2, a mating groove 5-3 is vertically disposed on the first side surface 5-7, a mating end surface 5-4 is disposed at the front end of the mating groove 5-3, a loading plane 5-5 is disposed at the bottom, and a first threaded hole 5-6 is disposed on a mating plate mating surface of the loading adapter 5. As shown in fig. 12, the two ends of the matching plate 6 are provided with second threaded holes 6-1, the middle part is provided with a limiting boss 6-2, and the near matching groove surface of the limiting boss 6-2 is provided with a limiting cambered surface 6-3. The second threaded hole 6-1 of the matching plate 6 is fixedly connected with the first threaded hole 5-6 of the loading adapter 5 through a first screw 7, and the limiting cambered surface 6-3 is matched with the matching groove 5-3 to limit the idler wheel 3.
As shown in fig. 6, the loading adapter (3) includes an upper adapter 8, an adapter limit clip 9, an adapter limit clip screw 10, and a lower adapter 11. As shown in fig. 13, the upper adaptor 8 is in an arch shape, a loading joint mounting groove 8-4 is formed in the inner side of the middle of the upper adaptor 8, first hinge shaft mounting grooves 8-1 are formed in two sides of the loading joint mounting groove 8-4 respectively, third threaded holes 8-2 are formed in the outer side of the first hinge shaft mounting groove 8-1, and first lugs 8-3 are arranged at two ends of the upper adaptor 8 respectively. As shown in fig. 14, one end of the adaptor limiting clip 9 is provided with an adaptor limiting clip screw hole 9-1, and the other end is provided with a limiting clip end face 9-2 matched with the first end face 5-2 and a first hinge shaft limiting cylindrical surface 9-3 matched with the first hinge shaft mounting groove 8-1. After the loading connector (2) is installed in the loading connector installation groove 8-4, the first hinge shaft 5-1 is arranged in the first hinge shaft installation groove 8-1 and the first hinge shaft limiting cylindrical surface 9-3, and the adapter limiting clamp screw hole 9-1 of the adapter limiting clamp 9 is connected with the third screw hole 8-2 through the adapter limiting clamp screw 10, so that the loading connector (2) and the upper adapter 8 are hinged into a whole through the first hinge shaft 5-1. As shown in fig. 15, the lower adaptor 11 is also in an arch structure, two ends of the lower adaptor 11 are respectively provided with a second lug 11-1, and a third lug 11-2 is arranged on the outer side of the middle of the lower adaptor 11. The upper adapter piece 8 and the lower adapter piece 11 are oppositely arranged, and the first lug piece 8-3 and the second lug piece 11-1 are detachably connected into a whole through the matching of bolts and nuts.
As shown in fig. 7, the loading control assembly (4) comprises a load cell 12, a wire rope 13 and a servo cylinder 14, wherein one end of the load cell 12 is hinged with a third lug of the down-turning piece 11, and the other end is connected with a piston rod of the servo cylinder 14 through the wire rope 13.
As shown in fig. 8, the fixed pulley assembly (5) comprises a fixed pulley 15, a pulley support 16, a pulley height adjusting plate 17 and a pulley support fixing upright 18 which are sequentially connected from top to bottom.
When the landing gear hook ring lock ring test loading device is used, the landing gear belt lock seat (1) stretches into a space formed by connecting the upper adapter 8 and the lower adapter 11, and the roller 3 on the landing gear lock column support 1 is inserted into the matching groove 5-3 of the loading adapter 5, so that the midpoint O of the loading plane 5-5 1 Is in contact fit with the outer cambered surface 3-1 of the roller 3. The width of the loading plane 5-5 along the axial direction of the rollerThe width of the lock hook is consistent with that of the hook ring lock. The upper adaptor 8 is hinged with the loading joint (2) through a first hinge shaft 5-1, the lower adaptor 11 is hinged with one end of a load cell 12 of the loading control assembly (4), the fixed pulley assembly (5) is installed below a steel wire rope 13 of the loading control assembly (4), and the pulley 15 supports the steel wire rope 13.
The connection relation of each part of the landing gear hook ring lock ring test loading device is further described as follows when the landing gear hook ring lock ring test loading device is used:
A. the loading joint (2) is hinged with a landing gear locking seat (only part of the landing gear) (1):
as shown in fig. 5 and fig. 9 to 11, the midpoint of the loading plane 5-5 contacts with the outer arc surface 3-1 of the roller 3, the distance L between the two first side surfaces 5-7 is equal, the first side surfaces 5-7 and the inner side surface 1-1 of the landing gear lock cylinder support 1 are matched and limited, and the interaction position and the point contact form of the lock hook to the lock ring in the using process are simulated;
as shown in fig. 5, the limit boss 6-2 of the matching plate 6 is inserted between two matching end faces 5-4 of the loading adapter 5, the roller 3 of the locking ring is clamped in the loading plane 5-5 and the limit cambered surface 6-3, and the translation of the loading adapter 5 around a plane perpendicular to the axis of the roller is limited; the first screw 7 is used for fixedly connecting the matching plate 6 with the loading adapter 5 through the matching groove 5-3 and the first threaded hole 5-6.
B. The loading joint (2) is hinged with the loading adapter (3):
as shown in fig. 6, the loading adapter 5 is hinged to the upper adapter 8. The two adaptor limiting clamps 9 are fixed on the upper adaptor 8 by the adaptor limiting clamp screw 10 through the adaptor limiting clamp screw hole 9-1 (see fig. 14) and the third screw hole 8-2 (see fig. 13), the first hinge shaft mounting groove 8-1 and the first hinge shaft limiting cylindrical surface 9-3 limit the first hinge shaft 5-1 (see fig. 10) therein, the upper adaptor 8 can rotate around the first hinge shaft 5-1, the rotational freedom degree of the upper adaptor 8 around the first hinge shaft 5-1 is released, additional bending moment is prevented from being brought to the locking ring due to loading direction deviation, and the accuracy of the test is improved.
C. The loading adapter (3) is connected with the loading control assembly (4) by bypassing the landing gear locking seat (landing gear only part) (1):
as shown in fig. 1, the upper adapter 8 bypasses the landing gear lock cylinder support (only part of the landing gear is shown) 1, and the upper adapter 8 and the lower adapter 11 are connected through the two first lugs 8-3 and the second lugs 11-1 of the lower adapter 11 (as shown in fig. 6). As shown in fig. 1, the loading adaptor (3) bypasses the landing gear lock cylinder support (landing gear only part is shown), and the loading control assembly (4) is used for pulling the adaptor (3), so that the scheme of loading the lock ring in a pushing mode is avoided.
As shown in fig. 7, the third lug 11-2 of the lower adaptor 11 is hinged to the load cell 12, the wire rope 13 connected to the load cell 12 bypasses the fixed pulley 15 to change direction and then is connected to the servo cylinder 14, and the output load of the servo cylinder 14 is matched with the load cell 12 to control the output load.
D. And (3) adjusting the height and the position of the fixed pulley assembly (5) and determining the test loading direction:
as shown in fig. 8, the fixed pulley 15 is fixed on the pulley support 16 by bolts, the pulley support 16, the pulley height adjusting plate 17 and the pulley support fixing upright 18 are connected by bolts, and the contact point O between the fixed pulley 15 and the wire rope 13 is realized by changing the pulley height adjusting plates 17 with different thicknesses 2 Height adjustment (see fig. 2); as shown in fig. 2 and 3, the left-right and back movement positions of the pulley support fixing upright post 18 are adjusted, so that after the included angle alpha between the lateral projection line of the lock cylinder axis direction B and the loading direction D is 90 degrees and the included angle beta between the stress direction C of the lock cylinder support and the projection line of the loading direction D on the loading plane 5-5 is 0 degrees, the pulley support fixing upright post 18 is fixedly connected with the ground.
When the landing gear shackle locking ring test loading device is used for experiments, the shackle locking ring loading method comprises the following steps:
as shown in fig. 4, the lock bolt 2 passes through a roller shaft hole 3-2 of the roller 3 and is fixed on the landing gear lock cylinder support 1 by the lock cylinder nut 4; as shown in fig. 5, the inner side surface 1-1 of the landing gear lock cylinder support 1 is matched with the first side surface 5-7 for limiting, and the distance L between the contact point of the loading plane 5-5 and the outer arc surface 3-1 of the roller 3 and the first side surface 5-7 is designed according to the requirement, so that the purpose of simulating the contact form and the load bearing position of the latch hook roller in the actual use process is achieved.
The loading joint (2) can rotate around the axis of the roller 3 and the lock stud 2, as shown in fig. 5, 10 and 11, and the loading joint (2) is hinged with the loading adapter (3) perpendicular to the first hinge shaft 5-1 in the axial direction of the roller 3 and the lock stud 2. As shown in fig. 2 and 3, the tangent point O between the wire rope 13 and the fixed pulley 15 is adjusted by adjusting the pulley fore-and-aft adjustment direction E and the pulley height adjustment direction F of the fixed pulley assembly (5) 2 Is relative to lock cylinder loading point O 1 To adjust the included angle alpha between the axial direction B of the lock cylinder and the lateral projection line of the loading direction D; and the fixed pulley component (5) is adjusted along the pulley left-right adjusting direction G so as to adjust the included angle beta of the projection line of the stress direction C of the lock column support and the loading direction D on the loading plane. According to the adjustment, the loading direction D is finally realized to meet the test requirement.
As shown in fig. 7, the servo cylinder 14 pulls the load cell 12 through the wire rope 13, and the load cell 12 pulls the load adapter (3) and applies a load to the roller (lock ring) 3 through the load joint (2). In this process, the magnitude of the output of the applied load is controlled in accordance with the detection value of the load cell 12.
While the invention has been described with reference to certain preferred embodiments, it will be understood by those skilled in the art that various changes and modifications may be made and equivalents may be substituted for elements thereof without departing from the scope of the invention. Therefore, any simple modification, equivalent variation and modification of the above embodiments according to the technical substance of the present invention shall fall within the scope of the technical solution of the present invention.
Claims (6)
1. The landing gear shackle lock ring test loading device is characterized by comprising a loading joint and a loading adapter;
the loading connector comprises a loading adapter (5) and a matching plate (6), wherein a matching groove (5-3) is formed in the loading adapter, a loading plane (5-5) is formed at the bottom of the matching groove, the matching plate is detachably connected with the loading adapter and fixes a lock ring of a hook-and-loop lock in the matching groove, the loading plane is in contact fit with the outer circular surface of the lock ring, the loading adapter is perpendicular to the first side surface of the lock ring axis and is matched with the inner side surface (1-1) of a landing gear lock column support (1), and the width of the loading plane along the axial direction of the lock ring is consistent with the width of a lock hook of the hook-and-loop lock;
the loading adaptor comprises an upper adaptor (8) and a lower adaptor (11), the upper adaptor and the lower adaptor are oppositely arranged and are detachably connected into a whole, a landing gear belt lock seat ((1)) of the landing gear lock column support is arranged in a space formed by surrounding the upper adaptor and the lower adaptor, the upper adaptor is hinged with the loading adaptor through a first hinge shaft (5-1), the lower adaptor is hinged with one end of a force transducer (12), and the other end of the force transducer is connected with a servo cylinder (14) through a steel wire rope (13).
2. Landing gear hook and loop lock catch test loading device according to claim 1, characterized in that a fixed pulley assembly is mounted under the near servo cylinder end of the wire rope, said fixed pulley assembly comprising a fixed pulley (15) for supporting the wire rope, a pulley support (16) for mounting the fixed pulley, a pulley height adjustment plate (17) mounted under the pulley support, a pulley support fixing post (18) mounted under the pulley height adjustment plate.
3. The landing gear shackle lock ring test loading device according to claim 2, wherein two ends of the loading adapter are provided with first end surfaces (5-2), two sides of the loading adapter are provided with first side surfaces (5-7), the outer sides of the first end surfaces are provided with the first hinge shafts, and the first side surfaces are vertically provided with the matching grooves.
4. The landing gear hook ring lock ring test loading device according to claim 3, wherein a matching end face (5-4) is arranged at the front end of the matching groove, a limiting boss (6-2) is arranged in the middle of the matching plate, a limiting cambered surface (6-3) is arranged on the near matching groove face of the limiting boss, the limiting boss is clamped into the matching groove, the side face of the limiting boss is matched with the matching end face, and the limiting cambered surface is matched with the matching groove to form a limiting space of the lock ring.
5. The landing gear hook ring lock ring test loading device according to claim 3, wherein a loading joint mounting groove (8-4) is formed in the inner side of the middle of the upper adapter, first hinge shaft mounting grooves (8-1) are formed in two sides of the loading joint mounting groove respectively, an adapter limiting clamp (9) is mounted outside the loading joint mounting groove, one end of the adapter limiting clamp is provided with a limiting clamp end face (9-2) matched with the first end face and a first hinge shaft limiting cylindrical surface (9-3) matched with the first hinge shaft mounting groove, and the first hinge shaft is arranged in a mounting space formed by the first hinge shaft mounting groove and the first hinge shaft limiting cylindrical surface in a matched mode, so that the loading joint and the upper adapter are hinged into a whole through the first hinge shaft.
6. A method of shackle loading experiments using the landing gear shackle locking ring test loading device as defined in any one of claims 3 to 5, wherein:
loading the landing gear with a lock seat into a space formed by surrounding the upper adapter and the lower adapter, clamping a lock ring on a landing gear lock column support into a matching groove of a loading head assembly, enabling a loading plane in the matching groove to be in contact fit with the outer circular surface of the lock ring, and designing a distance L between the contact point of the loading plane and the lock ring and a first side surface (5-7) of the loading adapter according to requirements so as to simulate the contact form of the lock ring in the actual use process;
the position and the height of the fixed pulley assembly are adjusted to adjust the position of a tangent point of the steel wire rope and the fixed pulley relative to a lock column loading point, so that the adjustment of an included angle alpha between a lateral projection line of a lock ring axis direction B and a loading direction D is realized, the adjustment of an included angle beta between a lock column support stress direction C and a projection line of the loading direction D on a loading plane is realized, and finally, the loading direction D meets the test requirement;
the servo cylinder pulls the load cell through a wire rope, the load cell pulls the load adapter, and applies a load to the lock ring through the load joint.
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| CN202210035789.9A CN114383934B (en) | 2022-01-10 | 2022-01-10 | Landing gear hook ring lock ring test loading device and method |
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| CN202210035789.9A CN114383934B (en) | 2022-01-10 | 2022-01-10 | Landing gear hook ring lock ring test loading device and method |
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| CN114383934A CN114383934A (en) | 2022-04-22 |
| CN114383934B true CN114383934B (en) | 2023-11-21 |
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| CN202210035789.9A Active CN114383934B (en) | 2022-01-10 | 2022-01-10 | Landing gear hook ring lock ring test loading device and method |
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Citations (21)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB639546A (en) * | 1947-01-30 | 1950-06-28 | Deryk Vaughan Jenkins | Improvements in, or relating to, toy aeroplanes or gliders |
| WO2000033649A1 (en) * | 1998-12-10 | 2000-06-15 | Isobe, Takao | Dog walking rope with extensible mechanism |
| CN102175415A (en) * | 2011-03-11 | 2011-09-07 | 江西洪都航空工业集团有限责任公司 | Undercarriage ship-off simulation experiment mechanism |
| JP2013010631A (en) * | 2011-06-30 | 2013-01-17 | Stas Co Ltd | Hanging metal fitting |
| CN103129749A (en) * | 2013-02-26 | 2013-06-05 | 西北工业大学 | Test rack for multi-point locking mechanisms |
| CN203681866U (en) * | 2013-04-24 | 2014-07-02 | 成都飞机设计研究所 | Side lock mechanism of unmanned aircraft landing gear |
| CN103983443A (en) * | 2014-05-21 | 2014-08-13 | 西北工业大学 | Horizontal testing device for reliability test of aircraft landing gear door uplock |
| CN103983444A (en) * | 2014-05-21 | 2014-08-13 | 西北工业大学 | Vertical testing device for reliability test of aircraft landing gear door uplock |
| WO2016070479A1 (en) * | 2014-11-06 | 2016-05-12 | 江西洪都航空工业集团有限责任公司 | Mechanical lock for landing gear and lock ring mechanism thereof |
| CN107264835A (en) * | 2017-07-13 | 2017-10-20 | 江西洪都航空工业集团有限责任公司 | A kind of gear test load charger |
| CN107651216A (en) * | 2017-10-23 | 2018-02-02 | 重庆通用航空产业集团有限公司 | Engine loading device and method applied to single-shot fixed wing aircraft slow test |
| CN108168854A (en) * | 2017-11-29 | 2018-06-15 | 中国航空工业集团公司沈阳飞机设计研究所 | A kind of aircraft nose landing gear outer barrel strut connector slow test fixture |
| CN207906685U (en) * | 2018-03-05 | 2018-09-25 | 浙江海伦塑胶有限公司 | A kind of wear-resistant pressure-resistant multi-deck extension water pipe |
| CN108801617A (en) * | 2018-06-12 | 2018-11-13 | 西北工业大学 | A kind of load-measuring device for cabin door lock reliability test |
| CN109969428A (en) * | 2019-02-28 | 2019-07-05 | 西安生淼机电科技有限责任公司 | A kind of aircraft nose landing gear uplock reliability and static strength/rigidity integrated experiment device and method |
| CN110763451A (en) * | 2019-11-15 | 2020-02-07 | 西北工业大学 | Cabin door lock reliability test device capable of controlling lock hook load and lock ring position |
| CN210240778U (en) * | 2019-07-25 | 2020-04-03 | 河北正祥市政工程有限公司 | Supporting device for installing drainage pipeline |
| CN111894350A (en) * | 2020-07-27 | 2020-11-06 | 浙江星洲航空科技有限公司 | Helicopter sliding cabin door locking mechanism |
| CN112378608A (en) * | 2020-11-25 | 2021-02-19 | 西安航天动力研究所 | Prestress-loaded rocket-borne equipment vibration test system and test method |
| CN112644692A (en) * | 2020-12-29 | 2021-04-13 | 中国航空工业集团公司西安飞机设计研究所 | Aircraft landing gear down position locking device |
| CN213283026U (en) * | 2020-07-24 | 2021-05-28 | 深圳迈瑞生物医疗电子股份有限公司 | Medical equipment's strutting arrangement and ultrasonic equipment |
Family Cites Families (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB0609049D0 (en) * | 2006-05-08 | 2006-06-14 | Airbus Uk Ltd | Method and apparatus for applying bending load to an axle of an aircraft landing gear |
| DE102010053277A1 (en) * | 2010-12-02 | 2012-06-06 | Airbus Operations Gmbh | Locking fixture, recliner fixture, component system, main wing of an aircraft wind tunnel model and aircraft wind tunnel model with such a main wing |
-
2022
- 2022-01-10 CN CN202210035789.9A patent/CN114383934B/en active Active
Patent Citations (21)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB639546A (en) * | 1947-01-30 | 1950-06-28 | Deryk Vaughan Jenkins | Improvements in, or relating to, toy aeroplanes or gliders |
| WO2000033649A1 (en) * | 1998-12-10 | 2000-06-15 | Isobe, Takao | Dog walking rope with extensible mechanism |
| CN102175415A (en) * | 2011-03-11 | 2011-09-07 | 江西洪都航空工业集团有限责任公司 | Undercarriage ship-off simulation experiment mechanism |
| JP2013010631A (en) * | 2011-06-30 | 2013-01-17 | Stas Co Ltd | Hanging metal fitting |
| CN103129749A (en) * | 2013-02-26 | 2013-06-05 | 西北工业大学 | Test rack for multi-point locking mechanisms |
| CN203681866U (en) * | 2013-04-24 | 2014-07-02 | 成都飞机设计研究所 | Side lock mechanism of unmanned aircraft landing gear |
| CN103983443A (en) * | 2014-05-21 | 2014-08-13 | 西北工业大学 | Horizontal testing device for reliability test of aircraft landing gear door uplock |
| CN103983444A (en) * | 2014-05-21 | 2014-08-13 | 西北工业大学 | Vertical testing device for reliability test of aircraft landing gear door uplock |
| WO2016070479A1 (en) * | 2014-11-06 | 2016-05-12 | 江西洪都航空工业集团有限责任公司 | Mechanical lock for landing gear and lock ring mechanism thereof |
| CN107264835A (en) * | 2017-07-13 | 2017-10-20 | 江西洪都航空工业集团有限责任公司 | A kind of gear test load charger |
| CN107651216A (en) * | 2017-10-23 | 2018-02-02 | 重庆通用航空产业集团有限公司 | Engine loading device and method applied to single-shot fixed wing aircraft slow test |
| CN108168854A (en) * | 2017-11-29 | 2018-06-15 | 中国航空工业集团公司沈阳飞机设计研究所 | A kind of aircraft nose landing gear outer barrel strut connector slow test fixture |
| CN207906685U (en) * | 2018-03-05 | 2018-09-25 | 浙江海伦塑胶有限公司 | A kind of wear-resistant pressure-resistant multi-deck extension water pipe |
| CN108801617A (en) * | 2018-06-12 | 2018-11-13 | 西北工业大学 | A kind of load-measuring device for cabin door lock reliability test |
| CN109969428A (en) * | 2019-02-28 | 2019-07-05 | 西安生淼机电科技有限责任公司 | A kind of aircraft nose landing gear uplock reliability and static strength/rigidity integrated experiment device and method |
| CN210240778U (en) * | 2019-07-25 | 2020-04-03 | 河北正祥市政工程有限公司 | Supporting device for installing drainage pipeline |
| CN110763451A (en) * | 2019-11-15 | 2020-02-07 | 西北工业大学 | Cabin door lock reliability test device capable of controlling lock hook load and lock ring position |
| CN213283026U (en) * | 2020-07-24 | 2021-05-28 | 深圳迈瑞生物医疗电子股份有限公司 | Medical equipment's strutting arrangement and ultrasonic equipment |
| CN111894350A (en) * | 2020-07-27 | 2020-11-06 | 浙江星洲航空科技有限公司 | Helicopter sliding cabin door locking mechanism |
| CN112378608A (en) * | 2020-11-25 | 2021-02-19 | 西安航天动力研究所 | Prestress-loaded rocket-borne equipment vibration test system and test method |
| CN112644692A (en) * | 2020-12-29 | 2021-04-13 | 中国航空工业集团公司西安飞机设计研究所 | Aircraft landing gear down position locking device |
Non-Patent Citations (2)
| Title |
|---|
| 一种起落架下位锁机构的设计;张航舟 等;机械工程师(第8期);第69-71页 * |
| 张航舟 等.一种起落架下位锁机构的设计.机械工程师.2018,(第8期),第69-71页. * |
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